US6835046B2 - Configuration of a coolable turbine blade - Google Patents

Configuration of a coolable turbine blade Download PDF

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Publication number
US6835046B2
US6835046B2 US10/311,935 US31193502A US6835046B2 US 6835046 B2 US6835046 B2 US 6835046B2 US 31193502 A US31193502 A US 31193502A US 6835046 B2 US6835046 B2 US 6835046B2
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US
United States
Prior art keywords
flow
trailing edge
duct
turbine blade
turbine
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Expired - Fee Related, expires
Application number
US10/311,935
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English (en)
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US20030156943A1 (en
Inventor
Michael Strassberger
Peter Tiemann
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Siemens AG
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Siemens AG
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: TIEMANN, PETER, STRASSBERGER, MICHAEL
Publication of US20030156943A1 publication Critical patent/US20030156943A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention generally relates to a turbine blade through which cooling fluid flows.
  • a turbine blade, through which cooling fluid flows, has internal flow ducts, which are separated from one another by internal walls.
  • the working fluid flows around the turbine blade.
  • the turbine blade can be a gas turbine blade.
  • the working fluid is then gas.
  • the turbine blade is inclined relative to the approaching working fluid, so that a force component in the peripheral direction of the turbine occurs in the usual manner.
  • the efflux direction of the working fluid is, therefore, essentially that direction along the turbine blade in which the working fluid flows around the latter.
  • the type mentioned is a turbine blade in the rear region of a turbine.
  • the working fluid has already expanded and cooled to such an extent that only slightly cooled turbine blades are employed.
  • only a small flow of cooling fluid through the turbine is provided. Because of the small flow, a meander structure of flow ducts for the cooling fluid does not function satisfactorily in the case of slightly cooled turbine blades.
  • the cooling fluid Because of the slow flow velocity of the cooling fluid, the latter would have an excessive cooling effect in the initial region of a meandering flow duct and would be too strongly heated in the final region, in consequence, the cooling effect would be inadequate in that region; in the case of the turbine blades mentioned, the flow velocity of the cooling fluid can also be too low with respect to the centrifugal forces occurring due to the rotation of the turbine.
  • the cooling fluid therefore only flows in a simple manner along the radial extent of the turbine blade.
  • simple flow i.e. in the case of flow ducts with practically no reversal locations relative to the radial direction of the cooling fluid flow—the problems mentioned above do not occur.
  • turbine blades which have radial holes or straight radial ducts extending from a radially inner blade root to outlet flow openings located further radially outward—outlet flow openings introduced into the rubbing edge.
  • the resulting cooling fluid flow then has the desired local—at each location of the flow duct—radial flow components which are expediently directed, predominantly to exclusively, radially outward.
  • An object of an embodiment of the present invention is to provide a turbine blade which, despite a small cooling fluid flow, is matched in terms of its geometry to the technical requirements for slightly cooled turbine blades and nevertheless permits substantially homogeneous cooling, in particular in the edge zones.
  • An embodiment of the invention offers the advantage that it permits a homogeneous cooling of the turbine blade, in particular in the region of the edges.
  • the advantage mentioned may be achieved by one or more trailing edge ducts being present whose cooling fluid flow have local transverse flow components at predetermined locations, outlet flow openings being introduced into a trailing edge of the turbine blade for these trailing edge ducts.
  • the use of the trailing edge as the region for the outlet flow of the cooling fluid opens a large variety of design possibilities, which were not previously accessible, for slightly cooled turbine blades.
  • the trailing edge ducts can—at least in part—conduct their cooling fluid away via the outlet flow openings which are introduced into the trailing edge.
  • outlet flow openings particularly on the rubbing edge, admission to which had previously been through the trailing edge ducts, can now be used for conducting away cooling fluid from flow ducts located in front of the trailing edge ducts.
  • a trebly useful effect is achieved: by this it is, namely, possible for the first time to effectively and homogeneously cool the trailing edge of a turbine blade according to an embodiment of the invention and to have, at the same time, a thin trailing edge (with respect to improved aerodynamics).
  • a natural efflux of the cooling fluid is achieved for the trailing edge ducts and this also permits the front flow ducts located in front of the trailing edge ducts to be matched, in their geometry and particularly in their efflux behavior, to the technical requirements.
  • front flow ducts can provide admission to more outlet flow length along the rubbing edge than was previously the case. Because the trailing edge ducts are, on the one hand, displaced further in the efflux direction toward the trailing edge and, on the other, are deflected due to their bent shape, the front flow ducts located in front of them can fill the resulting free space. Due to the local transverse flow components of the trailing edge ducts, the front flow ducts can likewise be bent in such a way that they also have local transverse flow components. This provides a different space utilization within the cooling volume of the turbine blade, with better utilization of the cooling air.
  • turbine blades in the rear region of the turbine i.e. turbine blades with little cooling
  • the other flow ducts, in particular the front and central flow ducts can be extended in this direction in terms of their extent parallel to the efflux direction and, therefore, can compensate for the decrease in thickness in the radial direction by spreading parallel to the efflux direction and utilizing a plurality of the outlet flow openings in the rubbing edge by use of a flow duct.
  • the flow ducts can be shaped in such a way that transverse flow components are present in the efflux direction and opposite to it. Exclusively or predominantly transverse flow components in the efflux direction are, however, preferred.
  • the transverse flow components effect a flow through the trailing edge, which was not previously present. Due to the utilization of the transverse flow components mentioned, furthermore, the cooling fluid is automatically conducted to the outlet flow openings in the trailing edge.
  • the deflection sections In order to avoid dead zones and to reduce the flow resistance overall, so that the total cooling volume available is effectively utilized, provision is made for the deflection sections to be rounded.
  • the deflection sections then extend without edges and with curvature.
  • a plurality of trailing edge ducts can be present.
  • the last trailing edge duct viewed in the efflux direction, is provided practically exclusively with outlet flow openings introduced into the trailing edge.
  • this is the most effective solution and as few outlet flow openings as possible—preferably no outlet flow openings at all—other than those of the trailing edge have fluid admitted to them and are, in consequence, occupied.
  • the last trailing edge duct can, therefore, also end before the rubbing edge radially inward at a radial distance. According to an embodiment of the invention, this duct needs, namely, no outlet flow openings in the rubbing edge at all. This first permits a particularly effective shaping of the turbine blade—in particular with respect to the efficiency of the turbine.
  • a radially continuous trailing edge duct can be present which has both outlet flow openings which are introduced into the rubbing edge and outlet flow openings which are introduced into the trailing edge.
  • Such a radially continuous trailing edge duct forms, more or less, the transition between a front flow duct and a trailing edge duct, which only has outlet flow openings which are introduced into the trailing edge. A gentle transition is achieved by use of such a radially continuous trailing edge duct.
  • the cooling volume available can be effectively utilized by this.
  • the last trailing edge duct prefferably has outlet flow openings which are located further radially inward and are introduced into the trailing edge and for the radially continuous trailing edge duct to have outlet flow openings which are located radially further outward and are introduced into the trailing edge.
  • An opening that is a penetration in the internal region between the two flow ducts, can be provided between the last trailing edge duct and the radially continuous trailing edge duct.
  • the wall between the individual flow ducts, which separates all flow ducts, is then interrupted at the location of the opening. The continuous connection is used to permit casting capability with respect to the core position.
  • an embodiment of the invention achieves the effect that the local, resultant, effective internal cross section is practically of the same size over the complete length of a flow duct with the exception of negligible cross-sectional deviations relating to the flow resistance of the flow duct.
  • the cross-sectional deviations are preferably less than 20 percent and, in particular, less than 10 percent, of the internal cross section mentioned.
  • the resultant, effective overall cross-sectional area of the inlet flow openings is preferably equal to the overall cross-sectional area of the outlet flow openings of a flow duct, the respective overall cross-sectional area corresponding to the internal cross section of the associated flow duct.
  • a turbine blade according to an embodiment of the invention has little cooling, i.e. is embodied without the meander structure of the flow ducts. It is used for the rear region of a turbine and/or for turbines/turbine blades with little cooling.
  • FIG. 1 shows a perspective elevation of a turbine blade according to an embodiment of the invention with blade root, the internally located flow ducts being represented as hidden,
  • FIG. 2 shows a longitudinal section through the turbine blade of FIG. 1 .
  • the working fluid 3 which is only represented as an excerpt and as an example in FIG. 1 —flows around the turbine blade 1 in the efflux direction 2 , the working power being generated, or the turbine driven, by this.
  • the cooling fluid 31 which is likewise shown as an excerpt and as an example in FIG. 2 —flows through the turbine blade 1 along the flow ducts 4 , 5 , 6 .
  • the turbine blade 1 is cooled by this.
  • the cooling fluid 31 can, for example, be (cooled) air.
  • Such a turbine blade 1 has a blade root 10 , which is pushed into a corresponding groove of the turbine disk (not shown here) and is fastened there.
  • the inlet flow openings 7 , 8 , 9 shown are aligned with corresponding openings in the turbine disk.
  • the cooling fluid 31 is supplied through these to the flow ducts 4 , 5 , 6 .
  • the flow ducts 4 , 5 , 6 extend between the inlet flow openings 7 , 8 , 9 on the radially inner blade root 10 and outlet flow openings 11 , 12 , 13 located opposite to them and radially further outward. They extend without reversal locations with respect to the radial direction 20 , i.e. practically reversal-free.
  • the cooling fluid 31 therefore, only flows simply through the radial extent of the turbine blade 1 in each flow duct 4 , 5 , 6 .
  • the resulting cooling fluid flow 14 has, locally, practically exclusively radially outwardly directed radial flow components 15 —and no approximately radially inwardly directed components (see FIG. 2 ).
  • All the radial flow components 15 therefore point away from the center of rotation of the turbine.
  • a turbine blade 1 then also has little cooling and is therefore suitable for realizing an embodiment of the invention if its flow ducts have, expediently, substantially radially outwardly directed radial flow components 15 .
  • the flow ducts 4 , 5 , 6 separated by the inner walls 30 are, in the exemplary embodiment shown, curved in such a way that the resulting cooling fluid flow 14 has local transverse flow components 17 in addition to the radial flow components 15 mentioned.
  • the resulting cooling fluid flow 14 in the flow ducts 4 , 5 is diagrammatically resolved in FIG. 2 into, respectively, a radial flow component 15 and a transverse flow component 17 .
  • the radial flow components 15 all point radially outward. In consequence, the cooling fluid flow 14 is practically reversal-free with respect to the radial direction 20 .
  • a last trailing edge duct 6 viewed in the efflux direction, is present.
  • This trailing edge duct 6 (like the flow ducts 4 , 5 also) deflects with rounded deflection sections 21 from the radial direction 20 into the efflux direction 2 .
  • the shape of the flow duct 6 is therefore curved in the direction toward the trailing edge 18 .
  • the transverse flow components 17 are locally directed in the efflux direction 2 at each location.
  • the cooling fluid 31 of the last trailing edge duct 6 is supplied to the outlet flow openings 13 in the trailing edge 18 , which outlet flow openings 13 are located further radially inward.
  • trailing edge ducts 5 , 6 are shown. Both trailing edge ducts 5 , 6 open into the outlet flow openings 13 , 23 in the trailing edge 18 .
  • the radially continuous trailing edge duct 5 opens into the outlet flow openings 23 , which are introduced into the trailing edge 18 and are located radially further outward, and simultaneously into an outlet flow opening 12 introduced into the rubbing edge 16 . So that the cooling fluid 31 in the radially continuous trailing edge duct 5 can be admitted to the outlet flow openings 23 located radially further outward, the last trailing edge duct 6 , viewed in the efflux direction 2 , ends radially inward in front of the rubbing edge 16 at a radial distance 22 . In consequence, there is no admission from the last trailing edge duct 6 to the outlet flow openings 23 .
  • the trailing edge ducts 5 , 6 communicate by way of an opening 24 , which is arranged in the center (relative to the radial direction 20 ) of the radially continuous trailing edge duct 5 and at the radially outer end of the last trailing edge duct 6 .
  • the front flow duct 4 viewed in the efflux direction 2 , becomes wider in the radial direction 20 toward the outside with respect to its extent in the efflux direction 2 (i.e. the width).
  • the front flow duct 4 also extends in a curved manner in such a way that local, resultant transverse flow components 17 are present.
  • the inner walls 30 which separate the flow ducts 4 , 5 , 6 from one another, are of practically the same thickness over the complete radial extent of the turbine blade 1 .
  • the shape of the front flow duct 4 therefore follows the trailing edge ducts 5 , 6 and nestles against these in such a way that the internal space of the turbine blade 1 is practically completely occupied by the flow ducts 4 , 5 , 6 .
  • trailing edge ducts 5 , 6 practically occupy the region of the trailing edge 18 of the turbine blade 1 with the exception of a residual, external wall thickness.
  • This wall thickness like, also, the size of the casting core of a cast turbine blade, i.e. the size of the hollow spaces—are limited in the downward direction by the technical parameters of the manufacturing process.
  • the occupancy of the trailing edge 18 also provides, overall, a homogeneous cooling, including the trailing edge 18 , of the turbine blade 1 .
  • the turbine blade 1 becomes narrower in the radial direction 20 toward the outside and simultaneously in the efflux direction 2 .
  • the internal cross section 25 of the flow ducts 4 , 5 , 6 should, however, remain approximately the same and, in fact, practically over the complete length 26 of a flow duct 4 , 5 , 6 . This is achieved for the first time, by an embodiment of the invention, for rear region turbine blades 1 .
  • the local, resultant, effective internal cross section 25 is practically the same size over the complete length 26 of a flow duct 4 , 5 , 6 with the exception of negligible cross-sectional deviations with respect to the flow resistance of the flow duct 4 , 5 , 6 . This is shown in FIG. 1, with the flow duct 4 as an example.
  • the area pieces 25 are simply shaded. They are intended to mark an equally large area within a flow duct in each case. In order to clarify the relationships, the areas are not reproduced to scale.
  • the area piece 25 is larger by the cross-sectional deviations 27 in the radial direction 20 .
  • the cross-sectional deviation 27 is preferably less than 20 percent, in particular less than 10 percent, of the internal cross section 25 .
  • this internal cross section 25 (not explicitly shown) should also remain the same. In order to achieve this objective, the front flow duct 4 widens in the radial direction 20 toward the outside.
  • Corresponding area pieces 25 of the trailing edge ducts 5 , 6 are shown. In these, it may be seen that the turbine blade 1 narrows in the efflux direction 2 . Viewed over a flow duct 4 , 5 , 6 , however, the internal cross section 25 should remain practically the same in the radial direction 20 , i.e. essentially in the direction of the shape of the respective flow duct 4 , 5 , 6 . This applies to the complete path of the flow fluid 31 within the turbine blade 1 from the blade root 10 to the outlet flow openings 11 , 12 , 13 , 23 .
  • the resulting, effective total cross-sectional area 28 of the inlet flow openings 7 , 8 , 9 is therefore equal to the total cross-sectional area 29 of the outlet flow openings 11 , 12 , 13 of a flow duct 4 , 5 , 6 .
  • This total cross-sectional area 28 , 29 then corresponds approximately to the internal cross section 25 of the associated flow duct 4 , 5 , 6 with the exception of the deviations mentioned above.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/311,935 2000-06-21 2001-06-08 Configuration of a coolable turbine blade Expired - Fee Related US6835046B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00113298 2000-06-21
EP001132298.4 2000-06-21
EP00113298A EP1167689A1 (de) 2000-06-21 2000-06-21 Konfiguration einer kühlbaren Turbinenschaufel
PCT/EP2001/006502 WO2001098634A1 (de) 2000-06-21 2001-06-08 Konfiguration einer kühlbaren turbinenschaufel

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US20030156943A1 US20030156943A1 (en) 2003-08-21
US6835046B2 true US6835046B2 (en) 2004-12-28

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US (1) US6835046B2 (de)
EP (2) EP1167689A1 (de)
JP (1) JP4683818B2 (de)
CN (1) CN1283901C (de)
DE (1) DE50115690D1 (de)
WO (1) WO2001098634A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060034690A1 (en) * 2004-08-10 2006-02-16 Papple Michael Leslie C Internally cooled gas turbine airfoil and method
US20060275125A1 (en) * 2005-06-02 2006-12-07 Pratt & Whitney Canada Corp. Angled blade firtree retaining system
US20080085193A1 (en) * 2006-10-05 2008-04-10 Siemens Power Generation, Inc. Turbine airfoil cooling system with enhanced tip corner cooling channel
US20090252603A1 (en) * 2008-04-03 2009-10-08 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US20110005196A1 (en) * 2009-07-10 2011-01-13 Andersen Leonard M Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
US20120272635A1 (en) * 2011-04-29 2012-11-01 Andersen Leonard M Gas Turbine Thrust Fuel Efficiency Enhancement System Water (Volatile) Introduction Arrangement Method and Means
US20120282110A1 (en) * 2009-12-31 2012-11-08 Snecma Inner ventilation blade
US20150192072A1 (en) * 2013-10-24 2015-07-09 United Technologies Corporation Fluid transport system having divided transport tube

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6955525B2 (en) 2003-08-08 2005-10-18 Siemens Westinghouse Power Corporation Cooling system for an outer wall of a turbine blade
RU2425982C2 (ru) * 2005-04-14 2011-08-10 Альстом Текнолоджи Лтд Лопатка газовой турбины
CN100368128C (zh) * 2006-04-03 2008-02-13 潘毅 透平动叶片铆钉头的加工方法
US7857587B2 (en) * 2006-11-30 2010-12-28 General Electric Company Turbine blades and turbine blade cooling systems and methods
CN101586477B (zh) * 2008-05-23 2011-04-13 中国科学院工程热物理研究所 一种具有射流冲击作用的扰流挡板强化传热装置
EP2971545B1 (de) * 2013-03-11 2020-08-19 United Technologies Corporation Mit niedrigem druckverlust gekühlte schaufel
EP3059394B1 (de) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Turbinenschaufel und Turbinenschaufelsatz
FR3096074B1 (fr) * 2019-05-17 2021-06-11 Safran Aircraft Engines Aube de turbomachine à bord de fuite ayant un refroidissement amélioré

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US2641440A (en) 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2687278A (en) 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US3017159A (en) 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3885609A (en) 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US4073599A (en) 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
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EP0034961A1 (de) 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gekühlte Gasturbinenschaufeln
GB2152150A (en) * 1983-12-27 1985-07-31 Gen Electric Anti-icing inlet guide vane
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure

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US5931638A (en) * 1997-08-07 1999-08-03 United Technologies Corporation Turbomachinery airfoil with optimized heat transfer
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Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641440A (en) 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2687278A (en) 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US3017159A (en) 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3885609A (en) 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US4073599A (en) 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4180373A (en) 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade
EP0034961A1 (de) 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gekühlte Gasturbinenschaufeln
GB2152150A (en) * 1983-12-27 1985-07-31 Gen Electric Anti-icing inlet guide vane
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7210906B2 (en) * 2004-08-10 2007-05-01 Pratt & Whitney Canada Corp. Internally cooled gas turbine airfoil and method
US20060034690A1 (en) * 2004-08-10 2006-02-16 Papple Michael Leslie C Internally cooled gas turbine airfoil and method
US20060275125A1 (en) * 2005-06-02 2006-12-07 Pratt & Whitney Canada Corp. Angled blade firtree retaining system
US7442007B2 (en) * 2005-06-02 2008-10-28 Pratt & Whitney Canada Corp. Angled blade firtree retaining system
US20080085193A1 (en) * 2006-10-05 2008-04-10 Siemens Power Generation, Inc. Turbine airfoil cooling system with enhanced tip corner cooling channel
US8246306B2 (en) 2008-04-03 2012-08-21 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US20090252603A1 (en) * 2008-04-03 2009-10-08 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US20110005196A1 (en) * 2009-07-10 2011-01-13 Andersen Leonard M Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
US8671696B2 (en) * 2009-07-10 2014-03-18 Leonard M. Andersen Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
US20120282110A1 (en) * 2009-12-31 2012-11-08 Snecma Inner ventilation blade
US20120272635A1 (en) * 2011-04-29 2012-11-01 Andersen Leonard M Gas Turbine Thrust Fuel Efficiency Enhancement System Water (Volatile) Introduction Arrangement Method and Means
US9376933B2 (en) * 2011-04-29 2016-06-28 Leonard M. Andersen Apparatus for distributing fluid into a gas turbine
US20150192072A1 (en) * 2013-10-24 2015-07-09 United Technologies Corporation Fluid transport system having divided transport tube
US9927123B2 (en) * 2013-10-24 2018-03-27 United Technologies Corporation Fluid transport system having divided transport tube

Also Published As

Publication number Publication date
JP2004501311A (ja) 2004-01-15
EP1292760B1 (de) 2010-11-03
JP4683818B2 (ja) 2011-05-18
CN1436275A (zh) 2003-08-13
DE50115690D1 (de) 2010-12-16
EP1167689A1 (de) 2002-01-02
WO2001098634A1 (de) 2001-12-27
US20030156943A1 (en) 2003-08-21
EP1292760A1 (de) 2003-03-19
CN1283901C (zh) 2006-11-08

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